EP4155581B1 - Polymergewindeeinsatz für hochlast-leitspindel und -mutter - Google Patents

Polymergewindeeinsatz für hochlast-leitspindel und -mutter Download PDF

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Publication number
EP4155581B1
EP4155581B1 EP22198371.1A EP22198371A EP4155581B1 EP 4155581 B1 EP4155581 B1 EP 4155581B1 EP 22198371 A EP22198371 A EP 22198371A EP 4155581 B1 EP4155581 B1 EP 4155581B1
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EP
European Patent Office
Prior art keywords
leadscrew
nut
insert
actuator
space
Prior art date
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Active
Application number
EP22198371.1A
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English (en)
French (fr)
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EP4155581A1 (de
Inventor
Navaneethakrishnan PANDIAN
Subrahmanyam VEERARAPU
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Hamilton Sundstrand Corp
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Hamilton Sundstrand Corp
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Publication date
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Publication of EP4155581A1 publication Critical patent/EP4155581A1/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
    • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
    • F16H25/20—Screw mechanisms
    • F16H25/24—Elements essential to such mechanisms, e.g. screws, nuts
    • F16H25/2427—Elements essential to such mechanisms, e.g. screws, nuts one of the threads being replaced by a wire or stripmetal, e.g. spring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
    • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
    • F16H25/20—Screw mechanisms
    • F16H25/24—Elements essential to such mechanisms, e.g. screws, nuts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
    • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
    • F16H25/20—Screw mechanisms
    • F16H25/24—Elements essential to such mechanisms, e.g. screws, nuts
    • F16H2025/249—Materials or coatings for screws or nuts

Definitions

  • the subject matter disclosed herein generally relates to leadscrews and nuts and, more particularly, to polymeric thread inserts for high load leadscrews and nuts.
  • Leadscrews and nuts may be used in aircraft and avionic application for various actuations. Such actuators can include, for example, doors, flaps, thrust reverses, and the like. Conventionally, such actuators may be formed of metallic leadscrews and nuts. However, such metal-to-metal configurations can cause excess wear and/or may require additional features, such as lubrication and the like.
  • One alternative to such metal-metal actuators is to use plastics. However, engineered plastic nuts against metallic leadscrews may have higher limiting pressure-velocity ("pv"), efficiency, low wear rate, etc., as compared to metal-metal configurations (e.g., bronze nut and metallic screws) in an unlubricated environment under low load application.
  • An alternative is to use a polymer nut with a metallic leadscrew, which due to their low wear behavior, may be considered as low a cost alternative to metallic ball screw based drives.
  • improved actuators that use a leadscrew-nut configuration may be beneficial.
  • leadscrew and nut actuators are provided.
  • the leadscrew and nut according to the invention includes a leadscrew having an external thread and formed from a first material, a nut configured to receive the leadscrew, the nut having an internal thread and formed from a second material, and an insert arranged between the internal thread of the nut and the external thread of the leadscrew, the insert configured to transfer force between the external thread and the internal thread and prevent material contact between the leadscrew and the nut.
  • the insert is formed of a third material different from the first material and the second material.
  • leadscrew and nut actuators may include that the first material and the second material are metals.
  • leadscrew and nut actuators may include that the first material and the second material are the same material.
  • leadscrew and nut actuators may include that the third material is a polymer.
  • leadscrew and nut actuators may include that the insert has a helical structure.
  • leadscrew and nut actuators may include that the insert is fixedly attached to the nut within the internal thread.
  • leadscrew and nut actuators may include that the insert is fixedly attached to the leadscrew within the external thread.
  • the actuator includes at least one end stop fixedly attached to the leadscrew and arranged within a space between axially adjacent portions of the external thread and configured to retain the position of the insert relative to the leadscrew.
  • the actuator according to the invention includes at least one end stop fixedly attached to the nut and arranged within a space between axially adjacent portions of the internal thread and configured to retain the position of the insert relative to the nut.
  • leadscrew and nut actuators may include that the external thread defines a space between axially adjacent portions of the external thread, wherein the space has a geometric profile and the insert has a cross-sectional shape that matches the geometric profile of the space.
  • leadscrew and nut actuators may include that the internal thread defines a space between axially adjacent portions of the internal thread, wherein the space has a geometric profile and the insert has a cross-sectional shape that matches the geometric profile of the space.
  • leadscrew and nut actuators may include that the insert has a rounded cross-sectional shape.
  • leadscrew and nut actuators may include that the insert has a squared cross-sectional shape.
  • leadscrew and nut actuators may include an additional insert arranged between the internal thread of the nut and the external thread of the leadscrew.
  • leadscrew and nut actuators may include that the leadscrew is operably connected to a component of an aircraft.
  • leadscrew and nut actuators may include that the nut is operably connected to a component of an aircraft.
  • leadscrew and nut actuators may include that at least one of the leadscrew and the nut are formed of a corrosion resistant steel, titanium, a non-corrosion resistant steel, and a copper based alloy.
  • leadscrew and nut actuators may include that the insert is formed from one of Polyamides, PEEK, PAEK, and PTFE.
  • leadscrew and nut actuators may include that the material of the insert includes a filler.
  • leadscrew and nut actuators may include that the filler comprises graphite or carbon.
  • the aircraft 100 includes a fuselage 102, wings 104, and a tail 106.
  • the aircraft 100 includes wing-mounted aircraft power systems 108.
  • the wing-mounted aircraft power systems 108 may be conventional gas turbine engines or other propulsion systems as known in the art.
  • aircraft employing embodiments of the present disclosure may include fuselage-mounted and/or tail-mounted configurations.
  • the aircraft power systems 108 may be used to generate thrust for flight and may also be used to generate onboard electrical power.
  • the aircraft 100 may also include one or more auxiliary power units 110 that may be configured to generate power.
  • the aircraft 100 includes doors 112 and aircraft flight control surfaces 114 (e.g., ailerons, flaps, flaperons, stabilizers, etc.). Additionally, the aircraft power systems 108 may include thrust reversers 116, as will be appreciated by those of skill in the art.
  • aircraft flight control surfaces 114 e.g., ailerons, flaps, flaperons, stabilizers, etc.
  • aircraft power systems 108 may include thrust reversers 116, as will be appreciated by those of skill in the art.
  • Actuators onboard aircraft can be used for, for example, actuating the doors 112, the flight control surfaces 114, the thrust reversers 116, landing gear, interior doors, seats, and the like.
  • the actuators may be configured as leadscrew and nut configurations. These actuators are typically linear actuators that rotate a nut to drive the leadscrew in an axial direction along an axis of the leadscrew.
  • FIG. 2 shows part of an engine housing 202 including a door 204 moveable between a closed position and an open position.
  • the door 204 is shown in its open position.
  • the actuator 200 is arranged to drive the door 204 between the closed position and the open position.
  • the actuator 200 is in the form of a linear actuator including a housing 206 that contains a nut 208.
  • the nut 208 is rotatable within the housing 206 and drives linear motion of a leadscrew 210. By rotating the nut 208, the leadscrew will translate, extension and retraction, to drive the door 204 between the closed position and the open position.
  • This type of actuation may be used for any controllable component onboard an aircraft, such as the various components described above and as appreciated by those of skill in the art.
  • the nut 208 may be formed of an engineered plastic that is arranged against a metallic leadscrew. Such a configuration may have higher limiting pressure-velocity ("pv"), efficiency, low wear rate, etc. as compared to metal-metal (e.g., bronze nut and metallic screw) configurations in an unlubricated environment under low load applications.
  • pv pressure-velocity
  • metal-metal e.g., bronze nut and metallic screw
  • polymer nuts with a metallic lead screw are considered low cost alternatives to metallic ball-screw based drives.
  • Such configurations are currently used for low load applications. It may be advantageous to incorporate polymers to improve operation of leadscrew-nut actuators.
  • Designing thread root features of plastics nuts for high load applications is a challenge due to their tensile and fatigue strength capability of polymer components.
  • contact pressure at a joint interface of a screw and a nut influences the friction coefficient and wear behavior of the interface, and such wear can cause early failure or shorten part life of such components.
  • a wide thread flank can reduce contact pressure at the interface, however, designing a wide flank is a challenge as it further worsens the stresses at the thread root features.
  • a machined or molded helical insert made of engineered polymers can be incorporated into a metal-metal actuator.
  • the insert When placed between a metallic nut and a metallic leadscrew, the insert can prevent metal to metal contact, thus enabling achieving a high load system that incorporates the advantages of a plastic or polymer system.
  • the insert(s) are held captive within the nut or to the leadscrew by mechanical or bonding means. Such captive inserts will prevent such inserts from winding out during actuation of the leadscrew.
  • multiple inserts can be assembled in series to share loads and thus increase an overall load capability of the system.
  • FIGS. 3A-3C schematic illustrations of an actuator 300 in accordance with an embodiment of the present invention are shown.
  • the actuator 300 may be configured for use onboard an aircraft and may be installed and arranged to enable actuation or operation of one or more components, systems, or devices onboard the aircraft.
  • the actuator 300 includes a leadscrew 302 and a nut 304.
  • the leadscrew 302 includes an external thread 306 and the nut 304 includes an internal thread 308.
  • the nut 304 is arranged within a housing 310. In some embodiments, the nut 304 is fixedly attached or connected to the housing 310.
  • the leadscrew 302 may be operably connected at one or both ends to surfaces and/or structures of an aircraft, with such surface and/or structure, or part thereof, configured to be moved or actuated by linear or axial movement of the leadscrew 302 along an axis A.
  • the nut 304 may be rotated to drive axial movement of the leadscrew 302.
  • the axial movement of the leadscrew 302 may drive rotation of the nut 304.
  • the component/structure/feature to be driven by the actuator 300 may be operably coupled to the nut 304 and/or the housing 310. It will be appreciated that the specific output operation (e.g., from leadscrew 302 or nut 304) is not intended to be limiting, but rather is reflective of the specific application and intended use of the actuator 300.
  • an insert 312 is arranged between the leadscrew 302 and the nut 304.
  • the insert 312 is configured to fit between the external thread 306 of the leadscrew 302 and the internal thread 308 of the nut 304.
  • the insert 312 may be formed of a material that is different from the material of each of the leadscrew 302 and the nut 304.
  • each of the leadscrew 302 and the nut 304 may be formed from a metal and the insert 312 may be formed from a polymer.
  • the metallic leadscrew 302 and nut 304 may be formed from steel (e.g., corrosion resistant or non-corrosion resistant), titanium, copper-based alloys, and the like and the insert 312 may be formed from virgin and filled grades of Polyamides, PEEK, PAEK, with fillers being, for example, graphite, carbon, and/or PTFE at various proportions to improve wear performance.
  • steel e.g., corrosion resistant or non-corrosion resistant
  • titanium e.g., copper-based alloys, and the like
  • the insert 312 may be formed from virgin and filled grades of Polyamides, PEEK, PAEK, with fillers being, for example, graphite, carbon, and/or PTFE at various proportions to improve wear performance.
  • FIG. 3B a schematic illustration of the leadscrew 302 with the insert 312 installed thereto is shown and FIG. 3C illustrates the insert 312 in isolation.
  • the external thread 306 of the leadscrew 302 forms a generally squared shape for a space 314 defined between axially adjacent portions of the external thread 306.
  • the insert 312 has a cross-sectional shape that matches or complements the shape of the space 314.
  • the insert 312 has a squared cross-sectional shape, as illustratively shown in FIG. 3C .
  • the insert 312 is fixedly attached to a specific portion of the leadscrew 302.
  • the attachment of the insert 312 to the leadscrew 302 may be by known means to enable attaching two different material components.
  • bonding, adhesives, mechanical fixing, or the like may be used to secure the insert 312 within the space 314 between the external thread 306 of the leadscrew 302.
  • one or more end stops 316 may be arranged at ends of the insert 312, as shown in FIG. 3B .
  • the end stops 316 may, in some embodiments, be formed of a material different from the leadscrew 302 and the insert 312.
  • the end stops 316 may be formed of metallic materials either chemically bonded or mechanically retained within or to the nut.
  • the end stops 316 may be fixedly attached or mounted to the leadscrew 302 and the insert 312 is not fixedly attached to the leadscrew 302. In such an embodiment, the end stops 316 may be used to maintain and hold the insert 312 in position relative to either the leadscrew 302 or the nut 304.
  • the insert 312 is attached to the leadscrew 302.
  • the insert 312 may be fixedly attached to the nut 304 and not attached to the leadscrew 302.
  • the configuration can include one or more end stops similar to that shown in FIG. 3B .
  • the insert 312 prevents direct material contact between the leadscrew 302 and the nut 304. As such, metal-to-metal contact may be avoided.
  • the insert 312 will transfer force between the external threads 306 of the leadscrew 302 and the internal threads 308 of the nut 304.
  • the insert 312 may be configured to enable transfer of high loads, such as about 1-20 kN (or about 200-4,500 lb) and speeds up to 0.5 m/s.
  • FIGS. 4A-4C schematic illustrations of an actuator 400 are shown.
  • the actuator 400 may be configured for use onboard an aircraft and may be installed and arranged to enable actuation or operation of one or more components, systems, or devices onboard the aircraft.
  • the actuator 400 is similar to that shown and described above with respect to FIGS. 3A-3C .
  • the actuator 400 includes a leadscrew 402 and a nut 404.
  • the leadscrew 402 includes an external thread 406 and the nut 404 includes an internal thread 408.
  • the nut 404 is arranged within a housing 410.
  • the leadscrew 402 may be operably connected at one or both ends to surfaces and/or structures of an aircraft, with such surface and/or structure, or part thereof, configured to be moved or actuated by linear or axial movement of the leadscrew 402 along an axis A.
  • the leadscrew 402 and the nut 404 may be rotated relative to each other to either rotate the nut 404 and/or drive axial movement of the leadscrew 402.
  • An insert 412 is arranged between the leadscrew 402 and the nut 404.
  • the insert 412 is configured to fit between the external thread 406 of the leadscrew 402 and the internal thread 408 of the nut 404.
  • the external thread 406 of the leadscrew 402 forms a generally rounded or circular shape for a space 414 defined between axially adjacent portions of the external thread 406.
  • the insert 412 has a cross-sectional shape that matches or complements the shape of the space 414.
  • the insert 412 has a circular cross-sectional shape, as illustratively shown in FIGS. 4A-4C .
  • no end stops are included.
  • the insert 412 may be fixedly attached (e.g., bonded or otherwise attached) to the leadscrew 402 or the nut 404, depending on the specific configuration to be implemented. Due to the direct attachment between the insert 412 and the other component, the end stops may be omitted.
  • the actuator 500 includes a nut 502 with an insert 504 installed thereto.
  • insert 504 is installed into a thread 506 of the nut 502.
  • the insert 504 is a two-start insert coil, having a first start 508 and a second start 510.
  • the insert 504 may be formed of two separate windings to accommodate the threads 506 (or configuration thereof) of the nut 502.
  • the insert 504 may be fixedly attached to the nut 502 by adhesive bonding 514, similar to that described above.
  • the insert 504 may be retained and positioned within the threads 506 of the nut 502 by one or more mechanisms, including the adhesive bonding 514.
  • additional retention and positioning features may include, for example, a grub screw installed tangential to helical coil/insert and/or inserts placed at the ends of the insert 504.
  • the nut 504 can include a cut outs with the inserts placed into the cutouts by approaching from either inside or outside and retained by a cylinder and screw shaft.
  • the inserts of the present invention may be machined or molded. As the inserts are installed about or within a thread of a leadscrew or nut, the inserts will have a helical structure having a defined cross-sectional shape/geometry to match or complement the thread. When placed between metallic nuts and leadscrews the inserts will prevent metal to metal contact. In the invention, the insert is held captive within the nut (e.g., by mechanical or bonding methods). This captive retention can prevent the inserts from winding out during actuation of the leadscrew. In some embodiments, multiple inserts may be arranged in sequence about the threads of the nut or leadscrew. This configuration can lead to a multi-start insert configuration that enables distribution or sharing of loads carried by the insert, thus increasing the overall load capability of the actuator.
  • the inserts for actuators described herein enable extending the benefit of a polymeric nut to higher load applications by using a polymeric insert arranged between metallic components (e.g., leadscrew and nut).
  • the inserts may be formed to tailor a flank width to reduce contact pressures, which in turn can result in lower pressure-velocity ("pv").
  • the inserts described can achieve longevity of actuators due to low wear behavior of the insert and avoidance of metal-to-metal contact/wear between threads of a leadscrew and a nut of the actuator.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)

Claims (15)

  1. Stellantrieb für Leitspindel und Mutter, Folgendes umfassend:
    eine Leitspindel (302), die ein Außengewinde (306) aufweist und aus einem ersten Material gebildet ist;
    eine Mutter (304), die dazu konfiguriert ist, die Leitspindel (302) aufzunehmen, wobei die Mutter (304) ein Innengewinde (308) aufweist und aus einem zweiten Material gebildet ist; und
    einen Einsatz (312, 412, 504), der zwischen dem Innengewinde (308) der Mutter (304) und dem Außengewinde (306) der Leitspindel (302) angeordnet ist, wobei der Einsatz (312, 412, 504) dazu konfiguriert ist, Kraft zwischen dem Außengewinde (306) und dem Innengewinde (308) zu übertragen und einen Materialkontakt zwischen der Leitspindel (302) und der Mutter (304) zu verhindern,
    wobei der Einsatz (312, 412, 504) aus einem dritten Material gebildet ist, das sich von dem ersten Material und dem zweiten Material unterscheidet,
    gekennzeichnet durch entweder
    mindestens einen Endanschlag (316), der an der Leitspindel (302) befestigt ist und in einem Raum zwischen axial benachbarten Abschnitten des Außengewindes (306) angeordnet ist und dazu konfiguriert ist, eine Position des Einsatzes (312, 412, 504) relativ zu der Leitspindel (302) beizubehalten, oder mindestens einen Endanschlag (316), der an der Mutter (304) befestigt ist und in einem Raum zwischen axial benachbarten Abschnitten des Innengewindes (308) angeordnet ist und dazu konfiguriert ist, die Position des Einsatzes (312, 412, 504) relativ zu der Mutter (304) beizubehalten.
  2. Stellantrieb für Leitspindel und Mutter nach Anspruch 1, wobei das erste Material und das zweite Material Metalle sind.
  3. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei das dritte Material ein Polymer ist.
  4. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei das erste Material und das zweite Material dasselbe Material sind.
  5. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei der Einsatz (312, 412, 504) eine spiralförmige Struktur aufweist.
  6. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei der Einsatz (312, 412, 504) fest an der Mutter (304) innerhalb des Innengewindes (308) befestigt ist oder wobei der Einsatz (312, 412, 504) fest an der Leitspindel (302) innerhalb des Außengewindes (306) befestigt ist.
  7. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei das Außengewinde (306) einen Raum zwischen axial benachbarten Abschnitten des Außengewindes (306) definiert, wobei der Raum ein geometrisches Profil aufweist und der Einsatz (312, 412, 504) eine Querschnittsform aufweist, die dem geometrischen Profil des Raums entspricht, oder wobei das Innengewinde (308) einen Raum zwischen axial benachbarten Abschnitten des Innengewindes (308) definiert, wobei der Raum ein geometrisches Profil aufweist und der Einsatz (312, 412, 504) eine Querschnittsform aufweist, die dem geometrischen Profil des Raums entspricht.
  8. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei der Einsatz (312, 412, 504) eine abgerundete Querschnittsform aufweist oder wobei der Einsatz (312, 412, 504) eine quadratische Querschnittsform aufweist.
  9. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, ferner einen zusätzlichen Einsatz (312, 412, 504) umfassend, der zwischen dem Innengewinde (308) der Mutter (304) und dem Außengewinde (306) der Leitspindel (302) angeordnet ist.
  10. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei die Leitspindel (302) mit einer Komponente eines Luftfahrzeugs wirkverbunden ist.
  11. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei die Mutter (304) mit einer Komponente eines Luftfahrzeugs wirkverbunden ist.
  12. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei mindestens die Leitspindel (302) und die Mutter (304) aus korrosionsbeständigem Stahl, Titan, nicht korrosionsbeständigem Stahl oder einer Legierung auf Kupferbasis gebildet sind.
  13. Stellantrieb für Leitspindel und Mutter nach einem der vorhergehenden Ansprüche, wobei der Einsatz (312, 412, 504) aus einem von Polyamiden, PEEK, PAEK und PTFE gebildet ist.
  14. Stellantrieb für Leitspindel und Mutter nach Anspruch 13, wobei das Material des Einsatzes (312, 412, 504) einen Füllstoff beinhaltet.
  15. Stellantrieb für Leitspindel und Mutter nach Anspruch 14, wobei der Füllstoff Graphit oder Kohlenstoff umfasst.
EP22198371.1A 2021-09-28 2022-09-28 Polymergewindeeinsatz für hochlast-leitspindel und -mutter Active EP4155581B1 (de)

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EP (1) EP4155581B1 (de)
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DE102023115079B3 (de) 2023-06-07 2024-10-17 ADMEDES GmbH Verfahren zur Herstellung eines Schraubgetriebes und Verfahren zur Herstellung eines Innengewindeteils

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FR3031564B1 (fr) 2015-01-12 2017-01-27 Peugeot Citroen Automobiles Sa Mecanisme de transformation d'un mouvement de rotation en un mouvement de translation par une liaison helicoidale de type a vis et ecrou
CN105864381A (zh) 2016-06-29 2016-08-17 北京邮电大学 一种改进的软轴螺旋传动装置
DE102017127750A1 (de) * 2017-11-23 2019-05-23 Böllhoff Verbindungstechnik GmbH Drahtgewindeeinsatz
EP3587864B1 (de) 2018-06-27 2021-05-05 Goodrich Actuation Systems Limited Kugelmutterschmierung
US11084603B2 (en) 2019-04-01 2021-08-10 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Brake key screw removal system and device

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BR102022018930A2 (pt) 2023-04-11
EP4155581A1 (de) 2023-03-29
CA3172920A1 (en) 2023-03-28
US20230111019A1 (en) 2023-04-13

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